Missile launcher



MISSILE LAUNCHER Fil'edJan. 9, 1961 2 Sheets-Sheet l I I la a: /a

NOR??? ZEN S B. A GHA/LES R. BROWN I WTO- solv 7. PRICE Fl 6. 2 BY M ATTORNEYS AGENT y 1 1963 z. B. ANDREWS ETAL 3,089,389

MISSILE LAUNCHER 2 Sheets-Sheet 2 Filed Jan. 9, 1961 FIG. 4

X%%% BROWN PRICE A T TORNE YS 441W fl/ZW FIG. 5

AGENT dfidiifid Patented May 14, 19%3 tic 3,0393% MISSILE LAUNQHEEK Zenas B. Andrews, Los Altos, Charies R. Brown, Sunnyvale, and Wilson T. Price, Santa Clara, Caiiil, assignors, by mesne assignments, to the United States of America as represented by the Secretary of the Navy Filed Jan. 9, 1961, Ser. No. 81,636 6 Ciaims. (til. 89-137) The present invention relates generally to missile launchers and more specifically to means for isolating a missile from vibration.

With the advent of ballistic missiles came the need for a method of making the missile launching complex invulnerable to surpise attack by enemy missiles and aircraft. Without such invuluerability it would be possible for a ballistic missile capability to be completely destroyed before its missiles could be launched in a retaliatory action. Further, without means to protect these launching complexes from destruction by enemy attack, they would be unable to fulfill their primary role of a deterrent to a possible enemy surprise attack.

Accordingly, several expedients have been the subject of extensive research and development. The three most prominent methods are firstly, the hardening of launching sites, for example, building concrete silos below ground level; secondly, by launching the missile from an airborne aircraft; and thirdly, by launching the missile from a moving ship or land vehicle. This invention finds use primarily in missile launchers of the third category. However, it cannot be said that the invention is inapplicable to the other two categories as it is possible that such a device could be utilized in conjunction with the launching of any ballistic or guided missile.

The missile launching systems which are mounted on vehicles usually are provided with a supply of missiles stored in a position which permits rapid firing. Such vehicles may have a tube-type launching system which includes one or more missile launching tubes, each having a missile positioned therein. The tube acts as a storing and conveying means as well as a launcher. Because these vehicles from time to time are subjected to substantial structural stressing and consequent structural flexing, the tube systems may comprise an outer tube which resiliently supports an inner tube in which the missile is positioned. The primary function of this dual tube system is to protect the missile from severe shocks generated by means other than the vehicle, for example, the depth charging of a submarine. To absorb these severe shocks, preloaded liquid springs may be used to support the inner tube within the outer tube. These springs are preloaded to such an extent that they normally act as a rigid connection between the inner and the outer tubes. Consequently, vehicle induced vibrations are not attenuated by the liquid springs but, to the contrary, are amplified as they pass through the missile launcher structure to the missile itself. The missile guidance system as well as many other missile components cannot withstand any substantial vibration without being adversely affected thereby. Consequently, these vibrations become a limiting factor in the performance of a vehicle launched missile system. Since these vibrations are primarily generated by vehicle movement, the speed of the vehicle must be substantially restricted in order to prevent vibration damage to the missile and its components. Restricting the speed of such a vehicle, obviously, greatly reduces its invulnerability.

Accordingly, one object of the present invention is to provide a means to protect a missile from launcher induced vibrations.

Another object of the present invention resides in the provision of a means which will attenuate vibrations being transferred to a missile from its launcher.

Still another object of the present invention is to provide a means to absorb vehicle induced vibrations in a missile launching system.

A further object of this invention is to provide a vibration absorbing means for a missile launching system which is reliable in operation and relatively inexpensive.

Other objects and many of the attendant advantages of this invention will be readily appreciated as the same becomes better understood by reference to the following detailed description when considered in connection with the accompanying drawings wherein:

FIG. 1 is a transverse cross-sectional view of a typical ballistic missile launching vehicle;

FIG. 2 is a sectional view substantially along the line 2-2 of FIG. 1;

FIG. 3 is a sectional view substantially along the line 33 of FIG. 3;

FIG. 4 is a sectional view substantially along the line 4-4 of FIG. 2; and

FIG. 5 is an exploded view of the lower portion of the flexure rod assembly illustrated in FIG. 4.

FIG. 1 illustrates one embodiment of the present invention, more specifically, it discloses a cross-sectional view of a ballistic missile launching submarine 11. As the missile launching systems 13 in the submarine 11 are identical the description which follows hereinafter will describe a single launching system.

A missile 12 is positioned in the missile launching systern 13 which has its upper portion covered by the hatch 14. Each missile launching system 13 includes an outer tube 15 which has resiliently mounted therein an inner tube 1%. The inner tube 16 and the outer tube 15 are provided with an opening 17 which is utilized to gain access to the missile guidance package, not shown. The missile 12 is ejected from the inner tube 16 when high pressure fluid is released from the flask 13. This fluid pressure is controlled by a fluid valve system, not shown, positioned in the conduit 39 which connects the fluid flask 18 with the lower portion of the launching system 13. Hydraulic springs 21 resiliently support the inner tube 16 Within the outer tube 15 thereby isolating the missile from sudden and severe shocks, for example, depth charges.

As illustrated in FIGS. 2 through 4 of the drawings, the missile 12, having missile skirt 3%, is vertically supported in the inner tube by support ring 31. The support ring 31 is resiliently secured to the lower end of the inner tube 16 by the flexure rod assembly 32, as best seen in FIG. 4. More specifically, the flexure rod 33 is securely and rigidly fastened by any conventional means 34 to the lower portion 35 of the inner tube 16. An elongated tubular shaped flexure rod housing 36 projects downwardly from the support ring 31 and is, as shown in FIG. 4, an integral part of the support ring 31. The flattened surfaces 4 2 at the extreme end of flexure rod 33 are suitable to receive a tool for the purpose of rotating the flexure rod in order to thread the upper end of the flexure rod into the lower end of the inner tube. Obviously, should another conventional fastening means be utilized for securing the flexure rod to the inner tube flattened surfaces as may become unnecessary.

Missile guide shoes or launch storage adapters 37, FIG. 3, are positioned between the missile and the inner tube at upper, lower, and intermediate points. Shoes 37 are utilized to laterally support the missile 12 in the inner tube 16 as Well as to reduce friction during launching of the missile. The flexure rod assembly 32 suspends the support ring 31 in a flexible manner below the lower portion of the inner tube 35 thereby permitting the missile 12 to be supported laterally by the launch storage adapters 37, thereby minimizing the lateral bending loads 3 applied to the missile skirt 30. When a sudden shock causes the vehicle 11 to be structurally flexed, the hydraulic springs 21 absorb the shock thereby substantially isolating the inner tube 16 and the missile 12 mounted therein from the severe shocks.

As mentioned hereinbefore, the hydraulic springs 21 are preloaded in order that they will absorb any severe shocks to which the vehicle 11 may be subjected thereby isolating the missile 12 from these shocks. However, for vehicle generated vibrations and slight shocks, the liquid springs 21 are substantially inoperable and the inner tube 16 is more or less rigidly secured within the outer tube 15. All vehicle generated vibrations are, therefore, transferred directly to the missile 12 thereby undesirably subjecting the sensitive missile components to these vibrations. These vibrations are most severe in the vertical direction as the vibration in the horizontal direction are somewhat attenuated by the launch storage adapters 37. To absorb or attenuate the vibrations in the vertical direction the present invention provides a vibration absorbing system in conjunction with the flexure rod assembly 32. At the lower end of the flexure rod 33 is mounted member 41 having an inverted T- shaped cross-section. Member 4-1 can obviously be an integral part of the fiexure rod or can be fastened thereto by conventional means, as shown in FIG. 5. Inverted T-shaped member 41 has a flange 43 projecting outwardly therefrom at its lower portion. At the outermost portion of the flange 43 is a projection 44 which is operable to contact the member 45. As will be described hereinafter, a substantially donut shaped member 47 composed of a vibration absorbing material is positioned around the member 41, as shown in FIG. 5. An inverted cupshaped member 45 is positioned above the vibration absorbing material in the manner shown also in FIG. 5. The cup-shaped member 45 has side portions 48 which restrain the outward lateral movement of the vibration absorbing material. The inverted T-shaped member 41 has side portions 49 which are operable to restrain the inward lateral movement of the vibration absorbing material. Bolt means 51 project through the flange portion 43, the vibration absorbing material 47, and the cup-shaped member 45, and into the lower portion of the flexure rod housing 36. Bolt means 51 threadedly engages only the lower portion of the flexure rod housing 36. Shims or spacers 52 are provided in order that the present invention might be readily adapted to existing equipment.

In operation, when vehicle inducted vibrations are transmitted from the outer tube 15 through the hydraulic springs 21 to the inner tube 16, through the flexure rod 33 to the flange 43, the vibration absorbing means 4-7 attenuates these vibrations thereby prohibiting their transmission to the flexure rod housing 36, the support ring 31, and the missile 12. Thus, it will be understood that there is no rigid metallic connection between the flexure rod 33 and the flexure rod housing 36 during normal operation. That is, there is no rigid connection between the flange 43 and the inverted cup-shaped member 45 through which vibrations may pass. The vibration of the flange member 43 attempts to pass through the vibration absorbing means 47 as the entire weight of the missile is being supported thereby. As explained hereinbefore, the vibration absorbing material, which may be any conventional vibration absorbing material, for example, rubber or metallic sponge material, attenuates or darnps these vibrations. When the missile launching system is subjected to severe shocks the inverted cup-shaped member 45 moves downwardly with respect to the flange member 43 until side portions 48 bottom against the projection 44- on the flange 43. In this bottomed position, the vibration absorbing material is substantially inoperative and the connection between the flcxure rod and its housing is substantially a rigid connection. When bottomed, the flexure rod is operable to absorb severe shock by allowing the support ring to move laterally with respect to the inner tube. Thus, when the system is subjected to severe shock, the vibration absorbing material advantageously reduces the jerk which occurs when the members and projection 44 are suddenly bottomed."

While the invention has been described with reference to a ballistic missile firing submarine, it is capable of being used in conjunction with any missile firing vehicle. The present invention enables such a vehicle to move at speeds which are unrestricted by vehicle generated vibrations.

Obviously many modifications and variations of the present invention are possible in the light of the above teachings. It is therefore to be understood that within the scope of the appended claims the invention may be practiced otherwise than as specifically described.

What is claimed is:

1. A missile launching system comprising an outer tube, an inner tube resiliently mounted within said outer tube in a manner to receive, support, and launch a missile, a support ring concentrically positioned adjacent the lower end of said inner tube, said support ring having an inner diameter which is smaller than the inner diameter of said inner tube thereby permitting said missile to contact said support ring when positioned in said inner tube, means resiliently securing said support ring to said lower end of said inner tube including a flexure rod having its upper end rigidly secured to said lower end of said inner tube, a flexure rod housing having its upper end rigidly secured to said support ring, means interconnecting the lower ends of said flexure rod and flexure rod housing in a manner to impede the transmission of vibration therethrough.

2. The system set forth in claim 1 wherein said flexure rod is concentrically positioned within said flexure rod housing, and said means interconnecting said lower ends includes a flange mounted on the lower end of said flexure rod, a vibration absorbing material interposed between said flange and said lower end of said flexure rod housing.

3. The system set forth in claim 2 wherein said means interconnecting said ends further includes restraining means operable to prohibit lateral movement of said vibration absorbing material, and fastening means securing said flange to said lower end of said flexure housing in a manner to permit a predetermined amount of vertical movement between said flange and said housing.

4. A missile launcher system operably mounted in a vehicle and operable to vertically launch a missile, comprising an outer tube operably mounted in said vehicle, an inner tube resiliently and concentrically mounted in said outer tube and operable to receive, laterally support, and launch said missile, a support ring concentrically positioned adjacent the lower end of said inner tube, said support ring having an inwardly projecting flange portion which extends laterally toward the axis of said tube, in a manner to vertically support said missile, a hollow tubular shaped flexure rod housing having its upper end rigidly secured to said support ring, a flexure rod concentrically positioned within said housing and having its upper end rigidly secured to said lower end of said inner tube, interconnecting means operable to connect the lower end of said housing and the lower end of said rod including vibration absorbing means operable to damp vibrations being transmitted through said interconnecting means whereby said support ring may move laterally with respect to said inner tube when said system is subjected to severe shock and said vibration absorbing means attenuates vehicle induced vibrations.

5. The missile launching system set forth in claim 4 wherein said interconnecting means further includes a flange mounted on the lower end of said flexure rod, said vibration absorbing means being interposed between said flange and said lower end of said flexure rod housing.

6. The missile launching system set forth in claim 5 wherein said vibration absorbing means is a vibration absorbing material, and said interconnecting means further includes restraining means operable to prohibit lateral movement of said vibration absorbing material, and fastening means securing said flange to said lower end of said housing in a manner to prohibit relative rotary and lateral movement while permitting a predetermined amount of vertical movement between said flange and said housing.

References Cited in the file of this patent UNITED STATES PATENTS Pointer Mar. 1, 1960 Ream et a1. Oct. 18, 1960 Dyson June 6, 1961 Siegel et a1. June 27, 1961 Werle et a1. Dec. 5, 1961 

4. A MISSILE LAUNCHER SYSTEM OPERABLY MOUNTED IN A VEHICLE AND OPERABLE TO VERTICALLY LAUNCH A MISSILE COMPRISING AN OUTER TUBE OPERABLY MOUNTED IN SAID VEHICLE, AN INNER TUBE RESILIENTLY AND CONCENTRICALLY MOUNTED IN SAID OUTER TUBE AND OPERABLE TO RECEIVE, LATERALLY SUPPORT, AND LAUNCH SAID MISSILE, A SUPPORT RING CONCENTRICALLY POSITIONED ADJACENT THE LOWER END OF SAID INNER TUBE, SAID SUPPORT RING HAVING INWARDLY PROJECTING FLANGE PORTION WHICH EXTENDS LATERALLY TOWARD THE AXIS OF SAID TUBE, IN A MANNER TO VERTICALLY SUPPORT SAID MISSILE, A HOLLOW TUBULAR SHAPED FLEXURE ROD HOUSING HAVING ITS UPPER END RIGIDLY SECURED T SAID SUPPORT RING, A FLEXURE ROD CONCENTRICALLY POSITIONED WITHIN SAID HOUSING AND HAVING ITS UPPER END RIGIDLY SECURED TO SAID LOWER END OF SAID INNER TUBE, INTERCONNECTING MEANS OPERABLE TO CONNECT THE LOWER END OF SAID HOUSING AND THE LOWER END OF SAID ROD INCLUDING VIBRATION ABSORBING MEANS OPERABLE TO DAMP VIBRATIONS BEING TRANSMITTED THROUGH SAID INTERCONNECTING MEANS WHEREBY SAID SUPPORT RING MAY MOVE LATERALLY WITH RESPECT TO SAID INNER TUBE WHEN SAID SYSTEM IS SUBJECTED TO SEVER SHOCK AND SAID VIBRATION ABSORBING MEANS ATTENUATES VEHICLE INDUCED VIBRATIONS. 